Assembly of turbine engine parts comprising a fan blade having an integrated platform, and corresponding turbine engine

Abstract

The invention relates to an assembly of turbine engine (50) parts having a longitudinal axis (X), the assembly comprising at least two adjacent fan blades made of a 3D woven composite material, each blade (1) comprising a root (3), a vane (2) extending from the root (3), and an integrated platform (4) inserted between the root (3) and the vane (2), the platform (4) extending on either side of the vane (2) and forming a pressure face platform portion (4I) and a suction face platform portion (4E), the pressure face and suction face platform portions of adjacent blades being connected by a fin (14) extending at least radially at the outer side of the pressure face and suction face platform portions (4I, 4E), relative to the longitudinal axis (X), having a substantially triangular transverse cross section and extending axially and so as to upper overlap the longitudinal edges (11A, 11B) of the pressure face and suction face platform portions (4I, 4E) of the adjacent blades.

Description

1. FIELD OF THE INVENTION[0001]The present invention relates to the field of turbine engines and in particular to dual-flow turbine engines in which the airflows circulate from upstream downstream. It relates more specifically, but not exclusively, to an assembly of turbine engine parts comprising fan blades having an integrated platform.2. PRIOR ART[0002]Dual-flow turbine engines comprise, in a known manner, a movable fan arranged upstream of a gas generator according to the circulation of gases in the turbine engine. The gas generator is housed in an annular inner casing while the fan is housed in an annular outer casing. Said inner and outer casings are separated by an annular inter-duct casing so as to delimit a primary duct and a secondary duct. The fan comprises a plurality of fan blades and a disc, from which each blade extends substantially radially. The free ends of the blades face the outer casing so as to compress an incident air flow at least in the secondary duct and, p...

AI Technical Summary

Benefits of technology

The present invention provides a solution to reduce the movements between the platforms of fan blades made of composite material while improving the aerodynamic aspect and limiting the impact on drag. This is achieved by adding a fin as an aerodynamic link system between the platforms. The fin helps limit opposing transverse movements between the platforms which cause aerodynamic leakages and guides and limits the passage vortices which are generated between the roots of the blades. The fin also reduces vibrations to which the integrated platform blades are subjected in the region of the platforms. The fin can be attached between the adjacent platforms or made up of two fin portions which improve the aerodynamic properties of the fan. The longitudinal edges of the pressure face and suction face platforms are the result of a non-interlinking of the 3D weave, which strengthens the platforms.

Problems solved by technology

The fan blade is a complex part, as its design requires a multi-disciplinary team which must cope at the same time with the aerodynamic, mechanical and acoustic aspects.

However, said blades may produce problems, for example manufacturing problems or problems of complying with requirements for assembly quality.

This could result in aerodynamic leakages and thus reduced performance.

Moreover, wear of the platforms at the junction thereof is a problem that must be considered.

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